US 11,774,098 B2
Combustor for a gas turbine engine
Pradeep Naik, Bangalore (IN); Rimple Rakeshkumar Rangrej, Bangalore (IN); Saket Singh, Bangalore (IN); Narasimha Chiranthan R, Bangalore (IN); Shai Birmaher, Cincinnati, OH (US); Hiranya Kumar Nath, Bangalore (IN); and Ravindra Shankar Ganiger, Bangalore (IN)
Assigned to GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Jun. 7, 2021, as Appl. No. 17/340,585.
Prior Publication US 2022/0390110 A1, Dec. 8, 2022
Int. Cl. F23R 3/08 (2006.01); F23R 3/16 (2006.01); F23R 3/00 (2006.01); F23R 3/06 (2006.01); F23R 3/34 (2006.01); F23M 5/08 (2006.01)
CPC F23R 3/16 (2013.01) [F23R 3/002 (2013.01); F23R 3/06 (2013.01); F23R 3/08 (2013.01); F23R 3/346 (2013.01); F23M 5/085 (2013.01); F23M 2900/05002 (2013.01); F23R 2900/00014 (2013.01); F23R 2900/03042 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor comprising:
a forward liner segment;
an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward liner segment and the aft liner segment at least partially defining a combustion chamber; and
a fence disposed between the forward liner segment and the aft liner segment, wherein the fence extends in the circumferential direction and extends into the combustion chamber along the radial direction, the fence comprising a main internal passageway extending from a cold side of the combustor to a hot side of the combustor and one or more secondary internal passageways branching off the main internal passageway, wherein the one or more secondary internal passageways comprise a plurality of internal passageways that converge.